How to Calculate Work on a Satellite in a Gravitational Field

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Homework Help Overview

The discussion revolves around calculating the work required to move a satellite from one circular orbit to another within a gravitational field, specifically from a radius of 2R to 3R. Participants are working with gravitational constants and energy equations relevant to orbital mechanics.

Discussion Character

  • Exploratory, Conceptual clarification, Mathematical reasoning, Problem interpretation

Approaches and Questions Raised

  • Participants explore different methods for calculating work, including energy calculations and integration approaches. Questions arise regarding the validity of initial kinetic energy assumptions and the application of potential energy equations. Some participants express confusion about the integration method and its effectiveness.

Discussion Status

The discussion is active, with various methods being proposed and critiqued. Some participants suggest that the original poster's approach is valid, while others emphasize the need for correct application of concepts. There is no explicit consensus, but multiple interpretations and methods are being explored.

Contextual Notes

Participants are working under the constraints of a homework problem, which may limit the information available for discussion. There are indications of confusion regarding the definitions of kinetic and potential energy in the context of orbital mechanics.

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Homework Statement



Given: The universal gravitational constant G = 6.67 E-11, the mass of the Earth M = 5.98E24, and its radius R = 6.7 E6. How much work must an external force do on the satellite to move it from a circular orbit of radius 2R to 3R, if its mass is 2000kg? Answer in Joules.


Homework Equations



I know that E = -GMm/2r, where M is the mass of the Earth and m = satellite.


The Attempt at a Solution


So I calculated the total energy in each radii,
for 2R, -GMm/4R
for 3R, -GMm/6R
then I subtract one from the other to get the net energy change. I don't know what to do after that. Please help. Thank you!
 
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There is a considerably simpler way of doing this. The work done in moving an object from one orbit to another is:

[tex]W=\int_{r_1}^{r_2} F(r) dr[/tex]

EDIT: Sorry forgot to say that your method is fine for potential energy not total mechanical energy as you have used.
 
Last edited:
thank you so much! :)
 
Kurdt said:
There is a considerably simpler way of doing this. The work done in moving an object from one orbit to another is:

[tex]W=\int_{r_1}^{r_2} F(r) dr[/tex]

EDIT: Sorry forgot to say that your method is fine for potential energy not total mechanical energy as you have used.

Actually, I think he is ok. The kinetic energy at radius R is GMm/(2R). The potential is -GMm/R. So the sum is, as he states, -GMm/(2R).
 
Was just the procedure in the attempt at the solution that made me think it was total mechanical energy.
 
I have the exact same question. This is one of the method that I used:
E intial = Ki + Ui = 0 + (-GMm/2R)
E final = Kf + Uf = (1/2)(GMm/3R) + (-GMm/3R)
then Work = E final - E intial

this make sense right? Then why it doesn't work

I also try the integrate method, but nothing work! Can somebody please tell me why?
and how to fix it?
 
If it's in orbit at radius 2R, how can Ki=0?
 
ok, so Ki is not = O; Then why is it the integration method didn't work either?
 
They both work. You just have to do them right.
 

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